Flying-machine.



G. H. CURTISS.

` FLYING MACHINE.

1,228,382; im Patented May 9, 1917. 4sHEETs su r1.

G. H. CURISS. FLYING MACHINE. APPLICATION FILED JULY 14,. |925.

Patented May 29, 191?.

4 SHEETS-SHEET 2.

I vente@ l G. H. curmss, FLYING MACHINE.

I APPLICATION FILED IULY I4, |9I5.. 1 ,228,382, Patented May 29,1917.

y 4 SHEETS-SHEET 3.

' G. H. CURTISS. FLYING MACHINE.

APPLICATION FIL-EI) JULY I4. ISIS, 1,228,382.

4 SHEETS--SHEET 4.

IIII

I Y r x I Ilyf" l j III I I V I I; II I 'la Patented May 29, 1917;

n UNITED sTATEs :PATENT oEEIcE GLENN n. CURTISS.' or BUFFALO, NEW Yonx, AssIGNon. To. THE cUETIss rroron'conr- PANY, or HAMMoNDSroET, NEW YORK, A. conr'onATIoN or NEW YORK.l

FLYING-MACHINE.

Specification of Letters Patent. A lladjendged May 29, 1917..

Application mea Jul'y 14, 1915. serial No. 39,836.Y

falo, in the countyof Erie and State of New rectional changes are carried out with more l York, have invented certain new and useful Improvements in Flying-Machines, of which the following' is a specification.

My invention relates t0,aeroplanes of the heavier-than-air type and has particularly to do with those types of aeroplanes intended to travel at relatively high speeds. For high speed work` it is essential that the machine be both reedof headresistant surfacesvor formations and be well balanced."Tlie rstessential makes directly for increase in rate of travel, while the second indirectly produces the same result, in that the machine is more responsive to its controls and itsdieiiiciency and at a higher rate of speed. My invention is lpossessed of thesespeed characteristics to a marked degree and yet its struc-l tural form is such that the body of the craft is also possessed of the `highest strength. Thus a craft built according to my invention travels at the very maximum possible speed with the very 'highest factor of safety.

A machine in which my invention is embodied is delineated in the accompanying drawings.

Figure 1 is a side elevation.

Fig. 2 is a top plan view.y

Fig. 3 is a front elevation.

Fig. 4 is an enlarged side elevation of the wheeled part of the landing gear.

Fig. 5 is aperspective view of an equalizing member of this gear from the inside.:

Fig. 6 is a transverse section of the same.

Figs. 7 and 8 are side and front elevations respectively of my invention as embodied in the flying boat. .p

Fig. 9 is a cross section of the bulwark of the boat Showing the termination of the vplanking short of the top and the light covering of the top of the boat.

Fig. 10 is a diagrammatic front elevation ofthe modiiied form of the landing gear.

Reference to the various parts ofthe machine is by means of the numerals designating them upon the drawings. Y p

(10) The main supporting surfaces of the craft, of which as shown, there are two', constituting, together, a biplane cell. Any s uit- V able number of supporting Surfaces, one or more, and arranged with respect to each other in suitable manner, may be used.

(11) Driving motors for the machine. rllhese driving motors are two in number in the embodiment shown, though there may be used one or more. In any case they are symmetrically disposed with respect to the vertical line passing through the center of lift of the main supporting surfaces or of the craft as a whole. This center of lift lies on thelongitudinal axis of the machine (inbe seen-that the motors 11 illustrated lie substantially parallel to and equidistant from this axis. Theyare supported in elevated positions midway between the supporting surfaces 10. lll'ney are of the tractor type, having propellers on their front ends as indicated and arranged to draw the machine forward through the air.

(12) A nacelle connected with the main supporting surfaces, in this instance below the lowermost one of them. lt is of streamline form, approximately symmetrically disposed with respect to a vertical line passing through the Acenter of lift.

(13) The approximate location of the vertical line passing through the center of lift.

(14, 15) Seats for passengers locatedin the nacelle. rllhe seats 14 are located in front of the tractor ends of the motors'll, while the seat 15 is located aft thereof. These seats, of which there may be one or more, in each case, are located also apl roximately symmetrically with respect to t e center of lift line 13. 15 is the pilots seat.

(16) The fuel supply tank located in the body of the nacelle intermediate the Seats 14, 15.

(17) An ammunition locker located intermediate the fuel supply tank- 16 and the front seats 14. Thecontents of the supply tank and the locker 17 are exhaustible and these are located in proximity and approximately symmetrically with respect to the center of lift line 13 whereby as the condicated by dotted lines Fig. 2) and it will tents are exhausted there is no disturbance A of the balance of the machine.

(18) Radiators for the motors located at l tapering from the point of greatest cross section at the radiators 18 to a point of minimum cross section aft of the motors.

(20) The engine beds.

(21) A pair of spars connected one to each engine bed and extending rearwardly in tapering form from ends ofthe engine beds 2O to which they are rigidly secured and in continuation of the streamline form of the housings 20 over the motors.

(22) A third spar similar to the spars of the pair 2l firmly secured to the rear end of the nacelle structure and extending rearwardly in continuation of the streamline form of the nacelle 12 and in a vertical plane midway between the spars of the pair 21, but somewhat below the same.

(23) A horizontal stabilizer supported in an approximately horizontal position by the outer ends of the pair 21.

, I (24) A transverse mainbeam of the stabilizer 23 to which 'the outer ends of the pair of spars 21 are connected.

(25) A vertical stabilizing surface supported between the after end of the spar 22 and the horizontal stabilizer 23.

(26) A vertical strut between spar 22 and the horizontal stabilizer 23. y

(27) A transverse beam in the body of the stabilizer itself, to which strut 26 is directly connected. Outer ends of beam 27 are con,- nected to the respective spars of the pair 21.

(28) A vertically extending rudder post between the extremity of spar 22 and the horizontal stabilizer beam 24.

(29) A vertical' rear rudder hinged lto rudder post 28.

(30) A pair ofelevator fia-ps one hinged to the horizontal stabilizer 23 on each side of rudder 29.

(31) Suitable cross wiring or bracing between spar 22 and the spars of pair 21 which makes of the whole a rigid rearwardly extending fuselage structure supporting the control surfaces '23, 25, 29, and 30 at its outer end.

(32) Axle members extending laterally in tandem pairs from the sides of the nacelle 12.. These axle members are hinged at their inner ends to the lnacelle whereby their outer ends may partake of movement in vertical planes.

(33) Tandem or following wheels mounted in pairs on the outer ends of the axles.

f (34) An equaliz'ing member interconnecting the tandem Wheels. The particular form of this member is immaterial. As shown it is a iexible, laminated bowspring whereby the equalizing connection becomes also a yielding connection. The top lamina-4 tion of this spring has two arches near its center. Y

(35) A pillar support depending from the supporting surface structure above the wheels and pivotally connecting with the y rearl seat, although :somewhat obstructed in equalizing member 34 at a point intermediate its ends. rlhe lower end of pillar 35 is convexed and bears against the arches of member 34 above mentioned. This member transmits the thrust of the landing gear directly to the main structure of the machine.

(36) A rearwardly extending brace to the end of the pillar support 35. Preferably the pillar support 35 is joined at its upper end to the front main beam of the supporting surface, while the upper end of the brace 36 is joined to the rear beam thereof in each t case. This structure is duplicated on opposite sides of the machlne.

(37) Strong cross wiring between the pillar support 35 and the sides of the nacelle structure. It will be observed that there is a pair of following wheels directly beneath each driving motor 11.. Y

(38) Driving motor supports in the same plane as the driving motors and the following wheels of the landing gear.

in operation as the machine is started from the ground into the air or alights upon the ground from the air the following wheels take up directly the impact of landing, the heavy masses of the driving motors being directly imposed upon them and the body structure being midwaykk between the pairs on opposite sides of the machine. The equalizing connections v. 34 between the wheels equalize the loads upon the individual wheels of the pairs, each wheel rising up and down with its axle and the pairs having oscillatory movement about the points of rocking or pivotal connection with the posts 35 as they pass over small or large obstructions. By virtue of this connection the machine is of an extremely easy riding nature on land, but of far more value than that, is the freedom of shock to vital parts and the extreme sturdiness of the gear itself.

Because the wheels are following or tandem they present a minimum' head resistance per air; P When the .machine is in the air, because of the streamline nature of the motor housings and nacelle and the longitudinal members of the fuselage structure in direct continuation thereof and approximately in lonv gitudinal parallelism, there is a very mimmum of drag. There are no projecting head resistant surfaces of an unuseful nature. Extreme speed is attainable under these conof being so trussed together (as indicated by the wires or braces 37) that the highest factor of safety desired may be attained.

By the/seat arrangement herein disclosed an unobstructed observation and gun fire range in both a vertical and a horizontal plane may be had from the forward seat through an arc of approximately one hundred and eighty (180) degrees'. The range from the ditions and yet the spars are so grouped (in ,their triangular arrangement) and capable a horizontal plane is approximately equal to that of the forward seat since said seats are located respectively in advance of and aft of the total supporting surface area of the machine. p

The embodiment of Figs. 7 and 8 is in the form of a flying boat.

(39) is the hull of the flying boat which is substituted for the nacelle 12 and the 'asso-4 of extremely light material such as alumi- A num, canvas or veneer planking. The tail of the boat takes the place of the spar 22 of the form of Figs. 1, 2 and 3 and is combined with the spars 21 to form thev fuselage structure supporting the control devices 23 to 30.

(4()V and 4l) Seats for passengers located respectively fore and aft of the main supporting surfaces 10, and approximately in the same relation to the remaining elements of the machine as seats 14 and 15. 41 is the pilots seat.

(42) Excrescent planing fins in extension of the bottom of the boatand constituting additional planing area.

(43) Bracing members between the lowermost supporting surface and these .fins whereby they are braced directly lto the supporting surfaces.

This flying boat possesses the same speed characteristics as the land machine hereinbefore described. The slim, streamlined body of the boat 39 takes the .place .of the nacelle 12 and spar 22 most effectively. Strength, efficiency of co'ntrol and speed are attained to an equal degree.

Fig. 10v discloses a modified form of landing gear for the land type of machine of Figs. 1 to 3. It differs from the form of Figs. 1 to 3 principally in that the axles 32 are carried to a point near the central plane of the nacelle and pivoted to an outward extension therefrom instead of to the bottom edges. The axles are then straight instead s rying controls and comprising a plurality of l longitudinal members extending one, at least, from each of the motors andthe na,- cele. l

3. Inan aeroplane, main supporting surfaces, a driving motor, a motor support, a

nacelle, and a fuselage 'structure including longitudinal members extended rearwardly as actual prolongations respectively of the motor support and of the nacelle, said members in each instance terminating forwardly in the vicinity of the aft end of the structure which they prolong.

4. In an aeroplane, main supporting surfaces, a driving motor mounted intermedi ate the supporting surfaces, motor supports interconnecting the respective supporting surfaces, engine bed beams interconnecting 'corresponding moto-r supports, rear controls,

and a longitudinal member extending rearwardly in prolongation of the engine bed beams to carry said rear controls.

5. In an aeroplane, a nacelle structure, twin driving motors mounted without, in a horizontal plane above and respectively at opposite sides of the nacelle, rear controls, and a longitudinal member extending rearwardly in prolongation of each motor and the nacelle, said members collectively constituting a fuselage structure for supporting the rear controls.

6. In an aeroplane, main supporting surfaces, a nacelle structure, a seat located in the nacelle forwardly of the total supporting surface area to provide an unobstructed observation range, and an unobstructed un fire arc of at least one hundred and eigty (180) degrees in both a vertical and horizontal plane, a seat located in said nacelle .aft of said total supporting surface area,

and a propelling means for the craft.

7. In an aeroplane, main supportingsurfaces, a nacelle structure having. an overall length sufficient to extend well beyond the total supporting surface areaboth fore and aft, a passengers seat located in the for- Wardly extended portion of the nacelle, a pilots seat located in the aft vextended portion of the nacelle, and a propelling means for the craft.

8. In an aeroplane, a nacelle structure, a seat located in the nacelle adjacent its forward end, supporting surfaces arranged to extend transversely across the nacelle aft of said seat, a tractor propellerv located intermediate said seat and said surfaces, a power plant, rear controls, and a longitudinal beam member extended aft from the rear of said nacelle to support said rear controls.

9. In an aeroplane, main supporting surfaces, a nacelle structure having an overall length suiiicient to extend Well beyond said supporting surfaces both fore and aft, aseat located in each of the extended portions of the nacelle, rear controls, a longitudinal susv ' surfaces to provide for both an unobstruct.

beam member extended aft from the rear end of the nacelle to support said rear controls, and a propelling means for the craft.

10. In an aeroplane, main supporting surfaces, a nacelle, a passengers seat located in the nacelle forwardly of the supporting ed observation range and for an unobstructed gun fire are of over 160 degrees in a horizontal plane, a pilots seat located in the nacelle aft of the supporting surfaces, and a propelling means for the machine .located aft of the passengers seat and forwardly of the pilots seat for operation in the horizontal plane above the nacelle.

11. In an aeroplane, in combination, main supporting surfaces, a tractor driving means, a seat for a passenger in front of the tractor end of said driving means, a seat for a passenger aft of the front end of said driving means, the location of said seats and driving meansl being such that the center of mass thereof lies in proximity to a vertical line passing through the center of pressure of said supporting surfaces.

12. In an aeroplane, main supporting surfaces, a plural number of flight resisting massesyarranged one above the other to support respectively the driving motor and the flying crew, an empennage, and longitudinal beam members extending aft respectively from at least two of said masses to collectively constitute a fuselage and support for the empennage.

13. In an aeroplane, main supporting sur# faces, driving motors therefor, spars extending .rearwardly from said driving motors, a body structure containing seats for passengers, ands giving a streamline rearward extension, and vertical and horizontal controls supported by the extension of said body structure and said spars in conjunction.

14:. In an aircraft, a nacelle, propelling means, a beam extending aft from the rear end of the nacelle, beams extending aft from the propelling means in a horizontal plane above the first mentioned beam, and a connection between the respective beams constituting therewith a fuselage for supporti ing the empennage of the aircraft.

15. In an aeroplane, main supporting surfaces, twin driving motors mounted one at neeaeea each side of the longitudinal axis of the aeroplane, a nacelle, and a fuselage supporting the rear controls and comprising beams extending aft from the respective motors and from the nacelle.

16. In an aeroplane, main supporting surfaces, a nacelle, a driving motor mounted in yond the leading edge of said supporting surfaces and aft" beyond the trailing edge thereof, propelling means mounted on opposite sides of the longitudinal axis of the machine and to operate in paths overlying the nacelle, and seats located in the nacelle respectively fore and aft the supporting surfaces and fore and aft the propelling means.

19. In an aeroplane, main supporting surfaces, horizontally disposed principal flight resisting masses arranged one above the other to support respectively the motor and the flying crew, rear controls, and means continuing said masses rearwardly in the form of beams to provide in effect a fuselage structure for the support of said rear controls, the fuselage structure at its forward end terminating aft of the vertical plane of the leading edge of said supporting surfaces.

20. In an aeroplane, main supporting surfaces, horizontally disposed principal flight resisting masses arranged one above the other to support respeetivelythe motor and the flying crew, rear controls, and means continuing said masses rearwardly to provide in effect and in a vertical plane a dual 'support for said rear controls.

In testimony whereof I allix my signature.A

GLENN H. CURTISS. 

